CN114580094B - Bird strike injury engineering prediction method for rotating state of metal blade - Google Patents

Bird strike injury engineering prediction method for rotating state of metal blade Download PDF

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CN114580094B
CN114580094B CN202210057899.5A CN202210057899A CN114580094B CN 114580094 B CN114580094 B CN 114580094B CN 202210057899 A CN202210057899 A CN 202210057899A CN 114580094 B CN114580094 B CN 114580094B
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blade
damage
bird strike
bird
energy
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CN114580094A (en
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罗刚
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Nanjing University of Aeronautics and Astronautics
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    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
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    • G—PHYSICS
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    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
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    • G06F30/00—Computer-aided design [CAD]
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    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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Abstract

According to the method for estimating the bird strike damage engineering in the rotating state of the metal blade, provided by the invention, the bird strike damage hidden danger and the estimated damage degree can be obtained by carrying out bird strike test on a real flat plate simulated blade to obtain data and drawing a continuous damage energy threshold-damage mode curve through a mathematical formula in combination with the data, wherein the data is used as a newly designed reference for judging whether the blade to be estimated has damage hidden danger or not, and the damage hidden danger and the estimated damage degree of the blade can be obtained by comparing the damage energy per unit area of the deformation energy of the blade at the impact position of the blade to be estimated with the continuous damage energy threshold-damage mode curve, so that the bird strike damage degree and the bird strike resistance of the metal blade can be determined simply, quickly and at low cost.

Description

Bird strike injury engineering prediction method for rotating state of metal blade
Technical Field
The invention relates to the field of engine blade damage tests.
Background
When the aeroengine works, birds are easily sucked into the aeroengine to cause impact damage of the engine blades, so that serious mechanical faults are caused, the bird impact resistance capability proposed by airworthiness regulations or design specifications must be met during design and evidence collection, and the metal blades still have wide application background in the current civil and military engine structure, so that the bird impact damage resistance capability of the metal blades is required to be improved along with the continuous improvement of the performance and safety requirements of the aeroengine and is embodied in early design. In the initial stage of metal blade design, mainly working as focusing on parameters such as blade profile and the like which influence performance indexes and corresponding design methods, aiming at the bird strike resistance of the blade, complex sample static/rotating state bird strike test and rotating state bird strike large-scale full-three-dimensional numerical analysis and evaluation are generally carried out after a blade design scheme is formed, the working difficulty is high, the cost is high, and a simple, convenient, quick and low-cost early engineering evaluation prediction method is lacked in the whole design period to preliminarily determine the bird strike damage degree and bird strike resistance of the blade, so that development is needed in related methods and processes.
Therefore, a new driving solution is needed to solve the above technical problems.
Disclosure of Invention
The invention aims to solve the problems of high difficulty, high cost, high risk and the like caused by the fact that a static/rotating state bird strike test and large-scale full-three-dimensional numerical analysis and evaluation of a blade sample can only be carried out in the current aircraft engine bird strike resistance design, and develops a metal blade rotating state bird strike resistance engineering prediction method based on static blade targeting and numerical simulation, so that the bird strike resistance degree and bird strike resistance of a metal blade can be determined simply, conveniently, quickly and preliminarily at low cost.
In order to achieve the above purpose, the method for estimating bird strike damage engineering in the rotating state of the metal blade provided by the invention can adopt the following technical scheme:
a method for estimating bird strike injury engineering in a metal blade rotation state comprises the following steps:
(1) Defining a bird strike continuous damage mode of the metal blade in a rotating state, and classifying the damage into j types of damage according to the light-to-heavy damage; j is a natural number greater than 1;
(2) Carrying out bird strike test on the flat plate simulation blade with the front edge characteristic in a static state, and manufacturing j bird strike damage flat plate simulation blades, wherein each bird strike damage flat plate simulation blade respectively forms a certain type of damage defined in the step (1);
(3) Establishing a bird strike finite element model of the flat simulation blade in a static state, performing numerical simulation, and calibrating a numerical simulation algorithm by adopting a test result;
(4) Adopting the verified simulation result of the bird strike value of the flat blade to extract and calculate the blade deformation energy IE in the bird strike process blade Total PE of system t The maximum deformation energy conversion η of (1), wherein:
η＝IE blade /PE t ；
(5) Obtaining the blade deformation energy IE of each damaged bird strike plate simulated blade by adopting the verified bird strike value simulation result of the plate blade j Calculating the unit area A of the blade section at the impact part i Lower injury energy threshold IE i Drawing a continuous injury energy threshold-injury mode curve, wherein:
IE i ＝IE j /A i the method comprises the steps of carrying out a first treatment on the surface of the Wherein i=j;
(6) Estimation of bird strike engineering for newly designed blades
6.1 According to the rotation linear speed of the impact point of the bladeDegree V blade Plan bird strike mass M bird And axial impact velocity V bird Computing a system total PE, wherein:
PE＝0.5*M bird *(V 2 bird +V 2 blade )
6.2 Conversion of blade deformation energy upper limit IE according to bird strike blade maximum deformation energy conversion rate eta max Wherein:
IE max ＝PE*η
6.3 According to the blade absorption upper energy IE max And the sectional area A 'of the impact position, calculating the damage energy IE' of the unit area of the deformation energy of the blade at the impact position of the blade to be estimated;
IE’＝IE max /A’
6.4 For the damage energy value IE' of the unit area of the section of the blade to be estimated and the damage energy threshold IE of the unit area i And comparing curves, judging that the blade cannot be damaged by visual impact if the IE ' energy value line falls below a threshold curve, judging the damage mode of the blade according to a continuous damage mode section where the intersection point is located if the IE ' energy value line intersects with the threshold curve, and judging that the blade is damaged by fracture if the IE ' energy value line exceeds the threshold curve.
The beneficial effects are that: according to the method for estimating the bird strike damage of the metal blade in the rotating state, large-scale full-three-dimensional numerical analysis and estimation are not needed, the bird strike damage test is conducted on a real flat plate simulated blade to obtain data, a continuous damage energy threshold-damage mode curve is drawn through a mathematical formula by combining the data, the data can be used as a new design reference for judging whether the blade to be estimated has damage hidden danger or not, the damage hidden danger and the estimated damage degree of the blade can be obtained by comparing the damage energy of the unit area of the blade deformation energy of the blade impact position to be estimated with the continuous damage energy threshold-damage mode curve, and the bird strike damage degree and the bird strike resistance of the metal blade can be determined simply, quickly and preliminarily at low cost.
Further, in the step (1), the damage is classified into six categories from light to heavy: slight bending (I), localized bulging (II), crack initiation (III), moderate crack propagation (IV), severe crack propagation (V), blade fracture (VI).
Further, in the step (2), after the two ends of the flat simulation blade are clamped by the clamp, the flat simulation blade is impacted by simulated bird bullets with different energies, so that six types of simulation blades in continuous damage modes are obtained.
Further, the continuous damage energy threshold-damage mode curve in the step (5) is drawn by adopting a two-dimensional coordinate system, wherein the horizontal axis is six types of damage from light to heavy, and the vertical axis is the damage energy threshold of the blade section.
Further, carrying out design correction of the newly designed blade according to the engineering estimation result in the step (6), and entering a next fine design iteration stage if the blade has stronger bird strike resistance; if the bird strike resistance of the blade is not strong, further taking design measures for enhancing the strength of the blade in the early design, and restarting the engineering estimation in the step (6).
Drawings
FIG. 1 is a graph of validated numerical simulation results of six classes of damaged flat simulated blades obtained from bird strikes.
Fig. 2 is a continuous damage energy threshold-damage pattern curve.
FIG. 3 is a schematic diagram of the estimation of the damage energy value IE' per unit area of the blade section to be estimated compared with the damage energy threshold IEi per unit area.
Detailed Description
The invention discloses a method for estimating bird strike damage engineering in a rotating state of a metal blade, and the technical scheme provided by the invention is described in detail below with reference to the accompanying drawings.
Examples of engineering evaluation methods for a certain titanium alloy blade are as follows:
(1) According to the use maintenance record, the case analysis and the early-stage research result, the bird strike continuous damage mode of the titanium alloy blade in the rotating state is defined as follows: slight bending (I) -localized bulge (II) -crack initiation (III) -moderate crack propagation (IV) -severe crack propagation (V) -blade fracture (VI);
(2) Bird strike test was performed in a stationary state on a flat plate simulated blade with a leading edge feature, and a bird strike flat plate simulated blade with the above-described typical features was manufactured. After the two ends of the flat simulation blade are clamped by the clamp, the flat simulation blade is impacted by simulated bird bullets with different energies, so that six types of simulation blades with continuous damage modes are obtained.
(3) And (3) establishing a bird strike finite element model of the flat plate simulation blade in a static state, performing numerical simulation, and calibrating a numerical simulation algorithm by adopting a test result, wherein reference is made to fig. 1 and 2.
(4) Therefore, the verified bird strike value simulation result of the flat blade is adopted to extract and calculate the blade deformation energy IE in the bird strike process blade Total PE of system t The maximum deformation energy conversion η of (1), wherein:
η＝IE blade /PE t
in this example, the maximum deformation energy conversion rate η of 6 kinds of damage is 17% to 20%, and hence η=0.2.
(5) Obtaining 6 blade deformation energy IE of typical damage of the bird strike blade by adopting the verified simulation result of the bird strike value of the flat blade j Calculating the unit area A of the blade section at the impact part i Lower injury energy threshold IE i Drawing a continuous injury energy threshold-injury mode curve, wherein:
IE i ＝IE j /A i
in this example, the IE is obtained by calculating and extracting the data i The values are shown in Table 1 and the threshold curves are shown in FIG. 2.
TABLE 1 blade section damage energy threshold
(6) Estimation of bird strike engineering for new design blade
1) According to the rotation linear velocity V of the impact point of the blade blade Plan bird strike mass M bird And axial impact velocity V bird Calculating total PE of the system, and calculating bird weight of 1kg under the condition of taking off according to the geometry of the bladeImpact blade middle parameter, calculated pe=19000J
2) Conversion of blade deformation energy upper limit IE according to bird strike blade maximum deformation energy conversion rate eta max Wherein:
IE max ＝3800J
3) According to the upper limit energy IE absorbed by the blade max And the sectional area A 'of the impact position, calculating the damage energy IE' of the unit area of the deformation energy of the blade at the impact position of the blade to be estimated;
IE’＝5.47J/mm2
5.47 > 4.5, so that the blade breaks at the impact location.
According to the same steps, the estimated result of blade damage of other mass birds under the same working condition is shown in fig. 3.
There are many ways in which the invention may be embodied, and the above description is only of a preferred embodiment of the invention. It should be noted that modifications and adaptations to the present invention may occur to one skilled in the art without departing from the principles of the present invention and are intended to be comprehended within the scope of the present invention. The components not explicitly described in this embodiment can be implemented by using the prior art.

Claims (5)

1. The method for estimating the bird strike injury engineering in the rotating state of the metal blade is characterized by comprising the following steps:
(1) Defining a bird strike continuous damage mode of the metal blade in a rotating state, and classifying the damage into j types of damage according to the light-to-heavy damage; j is a natural number greater than 1;
(2) Carrying out bird strike test on the flat plate simulation blade with the front edge characteristic in a static state, and manufacturing j bird strike damage flat plate simulation blades, wherein each bird strike damage flat plate simulation blade respectively forms a certain type of damage defined in the step (1);
(3) Establishing a bird strike finite element model of the flat simulation blade in a static state, performing numerical simulation, and calibrating a numerical simulation algorithm by adopting a test result;
(4) Bird strike count using validated flat bladeValue simulation result, extracting and calculating blade deformation energy IE in bird strike blade process blade Total PE of system t The maximum deformation energy conversion η of (1), wherein:
η=IE blade /PE t ；
(5) Obtaining the blade deformation energy IE of each damaged bird strike plate simulated blade by adopting the verified bird strike value simulation result of the plate blade j Calculating the unit area A of the blade section at the impact part i Lower injury energy threshold IE i Drawing a continuous injury energy threshold-injury mode curve, wherein:
IE i =IE j /A i the method comprises the steps of carrying out a first treatment on the surface of the Wherein i=j;
(6) Estimation of bird strike engineering for newly designed blades
6.1 According to the blade striking point rotation linear velocity V blade Plan bird strike mass M bird And axial impact velocity V bird Computing a system total PE, wherein:
PE=0.5*M bird *（V 2 bird +V 2 blade ）
6.2 Conversion of blade deformation energy upper limit IE according to bird strike blade maximum deformation energy conversion rate eta max Wherein:
IE max =PE*η
6.3 According to the blade absorption upper energy IE max And the sectional area A 'of the impact position, calculating the damage energy IE' of the unit area of the deformation energy of the blade at the impact position of the blade to be estimated;
IE’=IE max /A’
6.4 For the damage energy value IE' of the unit area of the section of the blade to be estimated and the damage energy threshold IE of the unit area i And comparing curves, judging that the blade cannot be damaged by visual impact if the IE ' energy value line falls below a threshold curve, judging the damage mode of the blade according to a continuous damage mode section where the intersection point is located if the IE ' energy value line intersects with the threshold curve, and judging that the blade is damaged by fracture if the IE ' energy value line exceeds the threshold curve.
2. The method for estimating bird strike injury engineering according to claim 1, wherein: in the step (1), the damage is classified into six types from light to heavy: slight bending (I), localized bulging (II), crack initiation (III), moderate crack propagation (IV), severe crack propagation (V), blade fracture (VI).
3. The method for estimating bird strike injury engineering according to claim 2, wherein: in the step (2), after the two ends of the flat simulation blade are clamped by the clamp, the flat simulation blade is impacted by simulated bird bullets with different energies, so that six types of simulation blades in continuous damage modes are obtained.
4. The method for estimating bird strike injury according to claim 3, wherein: the continuous damage energy threshold-damage mode curve in the step (5) is drawn by adopting a two-dimensional coordinate system, wherein the horizontal axis is six types of damage from light to heavy, and the vertical axis is the damage energy threshold of the blade section.
5. The method for estimating a bird strike injury according to any one of claims 1 to 4, wherein: and (3) carrying out design correction of the newly designed blade according to the engineering estimation result of the step (6).
CN202210057899.5A 2022-01-19 2022-01-19 Bird strike injury engineering prediction method for rotating state of metal blade Active CN114580094B (en)

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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110162821A (en) * 2019-03-08 2019-08-23 南京理工大学 A method of it calculating bird and hits high speed rotation engine blade
CN110362961A (en) * 2019-08-09 2019-10-22 中国航发沈阳发动机研究所 Aerial engine fan rotor blade bird impact tests parameter determination method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110162821A (en) * 2019-03-08 2019-08-23 南京理工大学 A method of it calculating bird and hits high speed rotation engine blade
CN110362961A (en) * 2019-08-09 2019-10-22 中国航发沈阳发动机研究所 Aerial engine fan rotor blade bird impact tests parameter determination method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
基于Logistic方法的鸟撞对飞行安全的影响分析;吴春波 等;航空发动机;第47卷(第6期);32-38页 *

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